Comparison of Concepts: Classic Jet Propulsion, Turbo-Electric Propulsion and Turbo-Hydraulic Propulsion

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Comparison of Concepts: Classic Jet Propulsion, Turbo-Electric Propulsion and Turbo-Hydraulic Propulsion ( comparison-concepts-classic-jet-propulsion-turbo-electric-pr )

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5.1.6 Direct Operating Costs 64 42.0 41.0 40.0 39.0 38.0 37.0 36.0 35.0 34.0 33.0 32.0 41.37 41.41 36.4 A320 36.7 38.2 TSTE2 38.36 38.43 35.6 TSTH2 TSTE4 Different Aircraft Configuration TPTH2 TPTE4 TPTH4 39.5 TSTH4 TPTE2 Figure 5.11 Different aircraft configurations vs direct operating costs (M$) A diverse set of parameters from aircraft design, influence the operating costs of an aircraft. From the graph, one can deduce that DOC increases with the number of engines. Also, TSTH2 aircraft has a lower DOC compared to A320 due to lower mass of engines and fuel consumption. A major drawback with all the proposed aircraft configurations, is that it is as- sumed that gas turbine engines are housed in the cargo compartment. This might initially lead to lack of cargo space and reduce revenue. 5.1.7 Overall Comparison In the Table 5.2, the important parameter for evaluating an aircraft is given with the deviation from the A320 model. While comparing all the parameters, TSTH2 is the best option. As dis- cussed before. The operating empty mass of TSTH4 is lower than A320. This means that the collective mass of 4 engines are less than the mass of two turbofan engines mainly due to the lower power requirement from each engine. The TSTH4, mainly satisfies the criteria by having the same number of flights per, flight and cruise speed. Since reduction in 𝑛 , can lead to reduction in revenue for aircraft operator or the airline. The result of the propeller driven aircraft is better than A320 due to the increase in bypass ratio. By installing one core engine, in this case the turboshaft engine, a propeller driv- en by a motor has a higher bypass ratio compared to a turbofan engine. Direct operating costs (M$)

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